Walter Mars I

For the larger 1930s 14-cylinder engine, see Walter Mars.

Mars I

Walter Mars I powered DAR 4 trimotor c.1930
Type	9-cylinder radial engine
National origin	Czechoslovakia
Manufacturer	Walter Engines
First run	c.1929

The Walter Mars I was a nine-cylinder, air-cooled, radial engine for aircraft use built in Czechoslovakia in the late 1920s.

Design and development

The Mars I was the largest capacity design of a series of three similar radial engines developed by the Walter company. Common cylinders were used for the five-cylinder Walter Vega and the seven-cylinder Walter Venus, the Mars I being a nine-cylinder engine.^[1]

Applications

Specifications

Data from Flight, July 1929.^[1]

General characteristics

Type: 9-cylinder radial engine
Bore: 105 mm (5.90 in)
Stroke: 120 mm (4.72 in)
Displacement: 9.352 L (570.7 cu in)
Dry weight: 159 kg (350 lb)

Components

Fuel system: Zenith Type 42 carburettor; two plugs/cylinder and twin Scintilla magnetos
Cooling system: Air-cooled
Reduction gear: Direct drive

Performance

Power output: 112 kW (150 hp)
Compression ratio: 5.15:1
Power-to-weight ratio: 0.72 kW/kg (0.43 hp/lb)

References

Wikimedia Commons has media related to Walter aircraft engines.

1 2 "Czechoslovakia". Flight. XXI: 762. 25 July 1929.

Walter aircraft engines

Engines	Atlas M208

Opposed engines	Atom M202

Inline engines	M 332 M 337 Junior Major Mikron Minor

V-12 engines	Sagitta

Radial engines	NZ 40 NZ 60 NZ 85 NZ 120 Bora Castor Gemma Jupiter Mars I Mars Merkur Pegas Polaris Pollux Regulus Scolar Super Castor Vega Venus

Turbojets	M05 M06 M701

Turboprops	H80 M601 M602

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